WO2016147032A1 - An ultra-high rpm rotatory system for propulsion in the vacuum of space - Google Patents

An ultra-high rpm rotatory system for propulsion in the vacuum of space Download PDF

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Publication number
WO2016147032A1
WO2016147032A1 PCT/IB2015/052107 IB2015052107W WO2016147032A1 WO 2016147032 A1 WO2016147032 A1 WO 2016147032A1 IB 2015052107 W IB2015052107 W IB 2015052107W WO 2016147032 A1 WO2016147032 A1 WO 2016147032A1
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WO
WIPO (PCT)
Prior art keywords
propulsion
speed
angular momentum
ultra
space
Prior art date
Application number
PCT/IB2015/052107
Other languages
French (fr)
Inventor
Korkut VATA
Original Assignee
Vata Korkut
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Vata Korkut filed Critical Vata Korkut
Priority to CN201580077773.2A priority Critical patent/CN107532575A/en
Priority to RU2017132304A priority patent/RU2017132304A/en
Publication of WO2016147032A1 publication Critical patent/WO2016147032A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/409—Unconventional spacecraft propulsion systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H99/00—Subject matter not provided for in other groups of this subclass
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • An ultra-high rpm rotatory turbine system for propulsion in the vacuum of space attains ultra high angular velocities and uses sparse gas molecules, electrons, photons as well as radiation as ejectory material to produce propulsion.
  • the system is continuously charged with electrical energy to preserve the ultra high angular momentum.
  • System of interest is controlled via the released amount of propellant gases and via the pitch of the blades for speed as well as for forward and reverse directions.
  • the system transforms ultra-high rpm angular momentum obtained by electrical energy into linear momentum upon accerelating gases and light weight material upto astronomical speeds.
  • the system works on the lower-end of gas pressure and related mass (passive propulsion) and on the higher-end (astronomical) of rotational speed.
  • the present invention relates generally to systems and methods for an ultra high rpm rotatory turbine system. More particularly, this invention pertains to a system and method for accerelating, traveling and curbing in space using an ultra high rpm rotatory tribune system.
  • the current invention aims to fulfill the need for a controllable propulsion system in space.
  • Current propulsion systems are either based on robust chemical combustion or on less powerful plasma-ion thrusters.
  • Ion thrusters have an input power spanning 1-7 kilowatts, exhaust velocity Of 20-50 kilometers per second, thrust of 20-250 millinewtons and an efficiency of 60-80% (1)
  • a chemical fuel based combustion engine can supply a thrust of 53,000 to 95,000 pounds-force (240 to 420 kN) (2).
  • a typical jet engine with turbines uses an hollow titanium fan blades with an internal Warren-girder structure to achieve strength, stiffness and robustness at low weight.
  • the blades can rotate at 3300 rpm with a tip speed of 1730 km/h, well above the speed of sound.
  • Laserdrilled holes are designed in the blades for cooling under the melting point of of the metal blades.
  • Plasma-ion systems have exhaust velocities of about 20-50 kilometers per second. However, they are on the lower end of thrust of about thrust 20-250millinewtons. According to Edgar Choueiri ion thrusters have an input power spanning 1-7 kilowatts, exhaust velocity 20-50 kilometers per second, thrust 20-250 millinewtons and efficiency 60-80%.
  • gas molecules can reach upto speeds of 10.000.000 meters /min within a 10.000.000 rpm system of 1 meters blade-tip circumference. 10.000.000 meters / min translates to a speed of 600.000 km an hour. 10kg of gas expelled at that speed can accerelate a 100 kg spacecraft upto a speed of 60.000 km / hour .
  • the invention of interest is unique and inventive in the sense that unlike chemial energy driven athmospheric turibine systems, the proposed system is driven electrically upto ultra high RPM levels in space and expells gases and other light weight material passively at astronomical speeds to create propulsion.

Abstract

Abstract: An ultra-high rpm rotatory turbine system for propulsion in the vacuum of space. The system attains ultra high angular velocities and uses sparse gas molecules, electrons, photons as well as radiation as ejectory material to produce propulsion. The system is continuously charged with electrical energy to preserve the ultra high angular momentum. System of interest is controlled via the released amount of propellant gases and via the pitch of the blades for speed as well as for forward and reverse directions. The system transforms ultra-high rpm angular momentum obtained by electrical energy into linear momentum upon accerelating gases and light weight material upto astronomical speeds. The system works on the lower-end of gas pressure and related mass (passive propulsion) and on the higher-end (astronomical) of rotational speed.

Description

AN ULTRA-HIGH RP ROTATORY SYSTEM FOR
PROPULSION IN THE VACUUM OF SPACE
Abstract: An ultra-high rpm rotatory turbine system for propulsion in the vacuum of space. The system attains ultra high angular velocities and uses sparse gas molecules, electrons, photons as well as radiation as ejectory material to produce propulsion. The system is continuously charged with electrical energy to preserve the ultra high angular momentum. System of interest is controlled via the released amount of propellant gases and via the pitch of the blades for speed as well as for forward and reverse directions. The system transforms ultra-high rpm angular momentum obtained by electrical energy into linear momentum upon accerelating gases and light weight material upto astronomical speeds. The system works on the lower-end of gas pressure and related mass (passive propulsion) and on the higher-end (astronomical) of rotational speed.
Background and Prior Art: The present invention relates generally to systems and methods for an ultra high rpm rotatory turbine system. More particularly, this invention pertains to a system and method for accerelating, traveling and curbing in space using an ultra high rpm rotatory tribune system.
The current invention aims to fulfill the need for a controllable propulsion system in space. Current propulsion systems are either based on robust chemical combustion or on less powerful plasma-ion thrusters. Ion thrusters have an input power spanning 1-7 kilowatts, exhaust velocity Of 20-50 kilometers per second, thrust of 20-250 millinewtons and an efficiency of 60-80% (1) A chemical fuel based combustion engine can supply a thrust of 53,000 to 95,000 pounds-force (240 to 420 kN) (2).
On the other hand a typical jet engine with turbines, uses an hollow titanium fan blades with an internal Warren-girder structure to achieve strength, stiffness and robustness at low weight. The blades can rotate at 3300 rpm with a tip speed of 1730 km/h, well above the speed of sound.
Laserdrilled holes are designed in the blades for cooling under the melting point of of the metal blades.
In such a system typically Airflow is approx. 1,440 kg (3,170 lb) per second and overall pressure ratio >=52: 1. http://en.wikipedia.org/wiki/Rolls-Royce_Trent (2)
Current exhaust velocities of jet systems are around 250 mph at the back of the airplane during take off
Plasma-ion systems have exhaust velocities of about 20-50 kilometers per second. However, they are on the lower end of thrust of about thrust 20-250millinewtons. According to Edgar Choueiri ion thrusters have an input power spanning 1-7 kilowatts, exhaust velocity 20-50 kilometers per second, thrust 20-250 millinewtons and efficiency 60-80%. (2)
Currently, space propulsion designs are based on rocket chambers without turbine systems. This patent application aims to fill the need for a ultra high rpm propulsion system in space. There are commercial electric motors available with an rpm range of 500.000 and 1.000.000 (4).
There are two restrictions on high rpm rotatory devices on earth First, airfriction impedes the rotation at high speeds and gravity in terms of one way force application on the system impedes the symmetry of the forces in high speed rotatory dynamics. However, in space these two impediments on rotatory motion are obsolete. Theoretically, the blade tips of an high rpm turbine can accelerate until the theoretical limits of the light speed given the necessary amount of energy in to the rotatory system. In the absolute vacuum and lack of gravity in space orders of magnitude higher rpm dynamics are achievable. Theoretically, in a turbine system in vacuum, gases can be accerelated upto the angular speed of the blade tips. We can say that gas molecules can reach upto speeds of 10.000.000 meters /min within a 10.000.000 rpm system of 1 meters blade-tip circumference. 10.000.000 meters / min translates to a speed of 600.000 km an hour. 10kg of gas expelled at that speed can accerelate a 100 kg spacecraft upto a speed of 60.000 km / hour .
Literally there is no limit for gas speeds in space. Supernova explosions expel much or all of the stellar material with velocities as much as 10% the speed of light, that is, about 30,000 km/s. These ejecta are highly supersonic: assuming a typical temperature of the interstellar medium of 0,000 K, the Mach number can initially be > 1000. (4)
Given the most recent developments in material science and 3D printing technologies there is no doubt that high heat resistant, strong materials are available for ultra high-turbine structure..
The invention of interest is unique and inventive in the sense that unlike chemial energy driven athmospheric turibine systems, the proposed system is driven electrically upto ultra high RPM levels in space and expells gases and other light weight material passively at astronomical speeds to create propulsion.

Claims

i Ini m :
1. An ultra high rpm tribune rotatory system driven by an electric motor in the vacuum of space and in zero gravity working on the logarithmic scale of 10A6, 10A7, 10A8 rpm and above.
2. The system accerelates to the targeted high rpm speed and angular momentum in vacuum and in zero gravity upon constant energy input.
3. The system has an internal gas chamber in between the rotatory blades, wherein propulsion material, hot and cold gases, plasma, radiation and such is released in a controlled fashion.
4. The system has a speed control and a direction control.
5. Claim of claim 4, wherein the speed and direction is controlled by blade pitch adjustment and wherein the blades can be rotated more than 90 degree perpendicular to the rotation axis, allowing reverse thrust without changing the direction of the angular momentum.
6. A claim of claim 4, wherein the speed is controlled by the amount of gas ( ejected mass per time), plasma, ion, as well as such charged and uncharged material released in to the gas chamber.
7. The system has an compression design towards the rear-end of the rotor pushing the gases to the blade tips with the highest angular momentum.
8. For particular applications, the high speed rotatory blades can be covered by mirrors and special reflective material to deflect the photons, charged particles and radiation of star-winds in the opposite direction whit a solid momentum to propel in the other direction.
9. For particular applications, the blades can be magnetized to drive propulsion from magnetic and electric fields in space.
10. For particular applications, the system with an empty internal gas chamber uses dispersed interstellar gas matter (mainly hydrogen) and accerelates the interstellar gas coming through the engine frontal opening through the rear end.
11. The system has a modular weight adjustment, wherein weight packages can be added and extracted on the rotatory system at the tribune null rotation state to fine-tune the rpm speed and angular momentum dynamics.
12. The system is used as a breaking device during planetary atmosphere entries as sparse atmospheric gases entering through the front-end increase the angular momentum of the system.
13. The system is used on slingshot approaches as a means of additional propulsion making use of the most outer, thin atmosphere of the planets.
14. At least two conter rotating ststems are used on a space vehicle to cancel out astronomical angular momentum and to stabilize the space vehicle.
PCT/IB2015/052107 2015-03-13 2015-03-23 An ultra-high rpm rotatory system for propulsion in the vacuum of space WO2016147032A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201580077773.2A CN107532575A (en) 2015-03-13 2015-03-23 A kind of ultrahigh speed rotary system promoted for space vacuum
RU2017132304A RU2017132304A (en) 2015-03-13 2015-03-23 ROTATING ULTRA-FREQUENCY FREQUENCY SYSTEM FOR BROADCASTING IN SPACE VACUUM

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2015953963 2015-03-13
TRPCT/TR2015/953963 2015-03-13

Publications (1)

Publication Number Publication Date
WO2016147032A1 true WO2016147032A1 (en) 2016-09-22

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Country Status (3)

Country Link
CN (1) CN107532575A (en)
RU (1) RU2017132304A (en)
WO (1) WO2016147032A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3919392A4 (en) * 2019-02-02 2022-10-05 Ningbo Institute of Materials Technology & Engineering, Chinese Academy of Sciences Method for flight on moon and lunar flight device

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10300621A1 (en) * 2003-01-10 2004-07-29 Georg Emanuel Koppenwallner Jet drive method for glider aircraft, water or air vehicle, model or toy, using fan system with one or more fan units for generating propulsion jets
WO2009065394A1 (en) * 2007-11-21 2009-05-28 Koppenwallner G E Blower arrangement for turbo machines
EP2253852A1 (en) * 2009-05-19 2010-11-24 Siemens Aktiengesellschaft Compressor assembly with an active magnetic bearing
US20140341706A1 (en) * 2013-05-14 2014-11-20 Dresser-Rand Company Supersonic compresor

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10300621A1 (en) * 2003-01-10 2004-07-29 Georg Emanuel Koppenwallner Jet drive method for glider aircraft, water or air vehicle, model or toy, using fan system with one or more fan units for generating propulsion jets
WO2009065394A1 (en) * 2007-11-21 2009-05-28 Koppenwallner G E Blower arrangement for turbo machines
EP2253852A1 (en) * 2009-05-19 2010-11-24 Siemens Aktiengesellschaft Compressor assembly with an active magnetic bearing
US20140341706A1 (en) * 2013-05-14 2014-11-20 Dresser-Rand Company Supersonic compresor

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3919392A4 (en) * 2019-02-02 2022-10-05 Ningbo Institute of Materials Technology & Engineering, Chinese Academy of Sciences Method for flight on moon and lunar flight device

Also Published As

Publication number Publication date
CN107532575A (en) 2018-01-02
RU2017132304A3 (en) 2019-07-24
RU2017132304A (en) 2019-04-15

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